I made simulation of flow around airfoil and I got very good results for AOA up to stall angle. I used SST model with gamma-theta transition model, y+ is less than 1 (about 0.75),... I tried with stady state simulation and also with transient but results were the same. Drag was near true but lift was too high because flow didn't separate. Can anybody tell me how can I improve results around stall angle!
Best Regards marek
Re: airfoil stall
A Reynolds averaged approach does not work well for a stalled airfoil. You need to go to LES or DES. Try either the SAS turbulence model or the DES model.
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